Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model ATP Airplanes, 8467-8471 [2010-3470]
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Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations
Office. The AMOC approval letter must
specifically reference this AD.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD, if it is approved by the
Boeing Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane and the
approval must specifically refer to this AD.
Material Incorporated by Reference
(i) You must use Boeing Alert Service
Bulletin MD90–53A031, dated April 10,
2009, to do the actions required by this AD,
unless the AD specifies otherwise.
(1) The Director of the Federal Register
approved the incorporation by reference of
this service information under 5 U.S.C.
552(a) and 1 CFR part 51.
(2) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, California 90846–
0001; telephone 206–544–5000, extension 2;
fax 206–766–5683; e-mail
dse.boecom@boeing.com; Internet https://
www.myboeingfleet.com.
(3) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(4) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
16, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3469 Filed 2–24–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0130; Directorate
Identifier 2009–NM–087–AD; Amendment
39–16214; AD 2010–05–05]
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RIN 2120–AA64
Airworthiness Directives; BAE
SYSTEMS (Operations) Limited Model
ATP Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
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ACTION: Final rule; request for
comments.
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above that would
supersede an existing AD. This AD
results from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
A review of the results of the final fuselage
fatigue test identified the need for additional
and revised safety-related fatigue- and
environmental inspections for the fuselage.
These additional tasks were introduced by
Service Bulletin (SB) ATP–51–002 * * *.
As it was determined that these
inspections were necessary to maintain the
structural integrity of the aeroplane, EASA
AD 2006–0090 [which corresponds to FAA
AD 2007–15–08] was issued * * *.
Since the original Issue of the SB, three
revisions have been published. Revision 1 of
the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage
frame designations in Parts 50 and 50A and
extended the allowable time before initial
inspection. In addition, the repeat inspection
interval in Part 43 of the SB was reduced. In
the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has
been clarified.
*
*
*
*
*
The unsafe condition is fatigue cracking
of certain structural elements, which
could result in reduced structural
integrity of the airplane and consequent
rapid decompression of the airplane.
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
March 12, 2010.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in the AD
as of March 12, 2010.
On September 21, 2006 (71 FR 52418,
September 6, 2006), the Director of the
Federal Register approved the
incorporation by reference of a certain
other publication listed in this AD.
We must receive comments on this
AD by April 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
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8467
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Todd Thompson, International Branch,
ANM–116, Transport Airplane
Directorate, FAA, 1601 Lind Avenue,
SW., Renton, Washington 98057–3356;
telephone (425) 227–1175; fax (425)
227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
On July 15, 2007, we issued AD 2007–
15–08, Amendment 39–15137 (72 FR
40230, July 24, 2007). That AD required
actions intended to address an unsafe
condition on the products listed above.
Since we issued AD 2007–15–08, the
European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0074,
dated March 31, 2009 (referred to after
this as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
A review of the results of the final fuselage
fatigue test identified the need for additional
and revised safety-related fatigue- and
environmental inspections for the fuselage.
These additional tasks were introduced by
Service Bulletin (SB) ATP–51–002, which
supplemented and in some cases revised
those previously published in the Aircraft
Maintenance Manual (AMM) Chapter 05–10–
17 and the Maintenance Review Board
Report (MRBR).
As it was determined that these
inspections were necessary to maintain the
structural integrity of the aeroplane, EASA
AD 2006–0090 [which corresponds to FAA
AD 2007–15–08] was issued to require the
inspections and, depending on findings,
corrective actions as defined in BAE Systems
(Operations) Limited SB ATP–51–002 (the
SB) at original issue.
Since the original Issue of the SB, three
revisions have been published. Revision 1 of
the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage
frame designations in Parts 50 and 50A and
extended the allowable time before initial
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inspection. In addition, the repeat inspection
interval in Part 43 of the SB was reduced. In
the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has
been clarified.
Fatigue tasks in Parts 1 through 50 of the
SB, i.e. those without an ‘‘A’’ suffix, have now
been replicated in AMM Chapter 05–10–17
and MRBR Section 6. In addition,
environmental tasks, those identified with an
‘‘A’’ suffix, have now been replicated in
MRBR Section 6.
For the reasons described above, this AD
retains the requirements of EASA AD 2006–
0090, which is superseded, and requires the
accomplishment of the inspections and,
depending on findings, corrective actions as
defined in BAE Systems (Operations) Limited
SB ATP–51–002 at Revision 3.
The unsafe condition is fatigue cracking
of certain structural elements, which
could result in reduced structural
integrity of the airplane and consequent
rapid decompression of the airplane.
The corrective actions include repairing
cracking and corrosion, and depending
on findings, repairing or replacing
damaged components. You may obtain
further information by examining the
MCAI in the AD docket.
different words from those in the MCAI
to ensure the AD is clear for U.S.
operators and is enforceable. In making
these changes, we do not intend to differ
substantively from the information
provided in the MCAI and related
service information.
We might also have required different
actions in this AD from those in the
MCAI in order to follow FAA policies.
Any such differences are highlighted in
a NOTE within the AD.
Change to Existing AD
This AD retains all requirements of
AD 2007–15–08. Since AD 2007–15–08
was issued, the AD format has been
revised, and certain paragraphs have
been rearranged. As a result, the
corresponding paragraph identifiers
have changed in this AD, as listed in the
following table:
REVISED PARAGRAPH IDENTIFIERS
Requirement in AD
2007–15–08
Corresponding
requirement in
this AD
paragraph (f)
paragraph (g)
paragraph (h)
paragraph (i)
paragraph (j)
paragraph (k)
paragraph (g).
paragraph (h).
paragraph (i).
paragraph (j).
paragraph (k).
paragraph (l).
Relevant Service Information
BAE SYSTEMS (Operations) Limited
has issued Service Bulletin ATP–51–
002, Revision 3, dated April 3, 2008.
The actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This AD
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This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
There are no products of this type
currently registered in the United States.
However, this rule is necessary to
ensure that the described unsafe
condition is addressed if any of these
products are placed on the U.S. Register
in the future.
Differences Between the AD and the
MCAI or Service Information
We have reviewed the MCAI and
related service information and, in
general, agree with their substance. But
we might have found it necessary to use
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FAA’s Determination of the Effective
Date
Since there are currently no domestic
operators of this product, notice and
opportunity for public comment before
issuing this AD are unnecessary.
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2010–0130;
Directorate Identifier 2009–NM–087–
AD’’ at the beginning of your comments.
We specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of those
comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this AD.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979); and
3. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
■
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
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§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Amendment 39–15137 (72 FR
40230, July 24, 2007) and adding the
following new AD:
■
2010–05–05 BAE Systems (Operations)
Limited: Amendment 39–16214. Docket
No. FAA–2010–0130; Directorate
Identifier 2009–NM–087–AD.
Effective Date
(a) This airworthiness directive (AD)
becomes effective March 12, 2010.
Affected ADs
(b) This AD supersedes AD 2007–15–08,
Amendment 39–15137.
Applicability
(c) This AD applies to all BAE Systems
(Operations) Limited Model ATP airplanes,
certificated in any category.
Note 1: This AD requires revisions to
certain operator maintenance documents to
include new and revised inspections.
Compliance with these inspections is
required by 14 CFR 91.403(c). For airplanes
that have been previously modified, altered,
or repaired in the areas addressed by these
inspections, the operator may not be able to
accomplish the inspections described in the
revisions. In this situation, to comply with 14
CFR 91.403(c), the operator must request
approval for an alternative method of
compliance according to paragraph (q) of this
AD. The request should include a description
of changes to the required inspections that
will ensure the continued damage tolerance
of the affected structure. The FAA has
provided guidance for this determination in
Advisory Circular (AC) 25–1529.
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Subject
(d) Air Transport Association (ATA) of
America Code: 51: Standard Practices/
Procedures.
Reason
(e) The mandatory continued airworthiness
information (MCAI) states:
A review of the results of the final fuselage
fatigue test identified the need for additional
and revised safety-related fatigue- and
environmental inspections for the fuselage.
These additional tasks were introduced by
Service Bulletin (SB) ATP–51–002, which
supplemented and in some cases revised
those previously published in the Aircraft
Maintenance Manual (AMM) Chapter 05–10–
17 and the Maintenance Review Board
Report (MRBR).
As it was determined that these
inspections were necessary to maintain the
structural integrity of the aeroplane, EASA
AD 2006–0090 [which corresponds to FAA
AD 2007–15–08] was issued to require the
inspections and, depending on findings,
corrective actions as defined in BAE Systems
(Operations) Limited SB ATP–51–002 (the
SB) at original issue.
Since the original Issue of the SB, three
revisions have been published. Revision 1 of
the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage
frame designations in Parts 50 and 50A and
VerDate Nov<24>2008
16:14 Feb 24, 2010
Jkt 220001
extended the allowable time before initial
inspection. In addition, the repeat inspection
interval in Part 43 of the SB was reduced. In
the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has
been clarified.
Fatigue tasks in Parts 1 through 50 of the
SB, i.e. those without an ‘‘A’’ suffix, have now
been replicated in AMM Chapter 05–10–17
and MRBR Section 6. In addition,
environmental tasks, those identified with an
‘‘A’’ suffix, have now been replicated in
MRBR Section 6.
For the reasons described above, this AD
retains the requirements of EASA AD 2006–
0090, which is superseded, and requires the
accomplishment of the inspections and,
depending on findings, corrective actions as
defined in BAE Systems (Operations) Limited
SB ATP–51–002 at Revision 3.
The unsafe condition is fatigue cracking of
certain structural elements, which could
result in reduced structural integrity of the
airplane and consequent rapid
decompression of the airplane. The
corrective actions include repairing cracking
and corrosion, and depending on findings,
repairing or replacing damaged components.
Compliance
(f) You are responsible for having the
actions required by this AD performed within
the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006–
18–09, With Revised Compliance Method
Airworthiness Limitations Revision
Specified in AD 2000–26–10
(g) Within 30 days after February 7, 2001
(the effective date of AD 2000–26–10,
Amendment 39–12060, which was
superseded by AD 2005–19–03, which was
superseded by AD 2007–15–08), revise the
Airworthiness Limitations Section (ALS) of
the Instructions for Continued Airworthiness
according to a method approved by the
Manager, International Branch, ANM–116,
Transport Airplane Directorate, FAA. Doing
the revision specified in paragraph (h) of this
AD replaces Chapters 27, 32, 53, and 54
listed in Section 05–10–11 and Chapters 52,
53, 54, 55, and 57 listed in Section 05–10–
17 that are in effect on February 7, 2001, with
Chapters 27, 32, 53, and 54 listed in Section
05–10–11, ‘‘Mandatory Life Limitations
(Airframe)’’; and Chapters 52, 53, 54, 55, and
57 listed in Section 05–10–17, ‘‘Structurally
Significant Items (SSIs)’’; both dated July 15,
2004; of the British Aerospace ATP Aircraft
Maintenance Manual (AMM). Doing the
revision specified in paragraph (l) of this AD
replaces Sections 05–10–12, 05–10–15, and
05–10–17 with the corresponding sections
specified in paragraph (l) of this AD.
Note 2: Guidance on revising the ALS can
be found in Section 05–00–00, dated August
15, 1997, of the British Aerospace ATP
AMM, dated October 15, 1999. This section
references other chapters of the AMM. The
applicable revision level of the referenced
chapters is that in effect on February 7, 2001.
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8469
Airworthiness Limitations Specified in AD
2005–19–03
(h) Within 30 days after September 28,
2005 (the effective date of AD 2005–19–03,
Amendment 39–14268, which was
superseded by AD 2006–18–09), revise the
ALS of the Instructions for Continued
Airworthiness according to a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA. Doing the revision
specified in paragraph (i) of this AD replaces
certain Chapter 52 and 53 tasks listed in
Section 05–10–17, ‘‘Structurally Significant
Items (SSIs),’’ dated July 15, 2004, of the
British Aerospace ATP AMM, with the
corresponding Chapter 52 and 53 tasks listed
in BAE SYSTEMS (Operations) Limited
Service Bulletin ATP–51–002, dated
December 20, 2005. Doing the revision
specified in paragraph (l) of this AD replaces
Chapters 52, 53, 54, 55, and 57 listed in
Section 05–10–17 with the corresponding
Section 05–10–17 specified in paragraph (l)
of this AD.
Note 3: Guidance on revising the ALS can
be found in Chapters 27, 32, 53, and 54 listed
in Section 05–10–11, ‘‘Mandatory Life
Limitations (Airframe)’’; and the tasks for
Chapters 52, 53, 54, 55, and 57 listed in
Section 05–10–17, ‘‘Structurally Significant
Items (SSIs)’’; both dated July 15, 2004; of the
British Aerospace ATP AMM. These chapters
replace the corresponding chapters in
Section 05–00–00, dated August 15, 1997, of
the British Aerospace ATP AMM as specified
in paragraph (g) of this AD.
New and Revised Airworthiness Limitations
in AD 2006–18–09
(i) Within 30 days after September 21, 2006
(the effective date of AD 2006–18–09), revise
the ALS of the Instructions for Continued
Airworthiness by incorporating the new and
revised tasks for Chapters 52 and 53 as
specified in BAE SYSTEMS (Operations)
Limited Service Bulletin ATP–51–002, dated
December 20, 2005, into the ALS. The
revised Chapter 52 and 53 tasks replace the
corresponding Chapter 52 and 53 tasks in
Section 05–10–17, ‘‘Structurally Significant
Items (SSIs),’’ dated July 15, 2004, of the
British Aerospace ATP AMM, as specified in
paragraph (h) of this AD.
(j) Except as provided by paragraph (q) of
this AD: After the actions specified in
paragraphs (g), (h), and (i) of this AD have
been accomplished, no alternative
inspections or inspection intervals may be
approved for the structural elements
specified in the documents listed in
paragraphs (g), (h), and (i) of this AD.
No Reporting Required
(k) Although BAE SYSTEMS (Operations)
Limited Service Bulletin ATP–51–002, dated
December 20, 2005, specifies to submit
certain information to the manufacturer, this
AD does not include that requirement.
Restatement of Requirements of AD 2007–
15–08, With Revised Compliance Method
Revised Limitations
(l) Within 30 days after August 8, 2007 (the
effective date of AD 2007–15–08), revise the
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ALS of the Instructions for Continued
Airworthiness according to a method
approved by the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA.
Note 4: Guidance on revising the ALS can
be found in Section 05–10–12, ‘‘Mandatory
Life Limitations (Airframe—Structures),’’
dated January 15, 2007; Section 05–10–15,
‘‘Mandatory Life Limitations (Powerplant/
Engine/APU—Structures),’’ dated January 15,
2007; and Section 05–10–17, ‘‘Structurally
Significant Items (SSIs),’’ dated January 15,
2007; of the BAE Systems (Operations)
Limited ATP AMM. The revised sections
replace the corresponding sections specified
in paragraphs (g) and (h) of this AD.
(m) Except as provided by paragraph (q) of
this AD: After the action specified in
paragraph (l) of this AD has been
accomplished, no alternative inspections or
inspection intervals may be approved for the
structural elements specified in the
documents listed in paragraph (l) of this AD.
New Requirements of This AD
Actions
(n) Within 30 days after the effective date
of this AD: Revise the ALS of the Instructions
for Continued Airworthiness by
incorporating the inspections specified in
BAE SYSTEMS (Operations) Limited
Inspection Service Bulletin ATP–51–002,
Revision 3, dated April 3, 2008. Doing this
revision terminates the requirements of
paragraph (i) of this AD. The revised Chapter
52 and 53 tasks replace the corresponding
Chapter 52 and 53 tasks in Section 05–10–
17, ‘‘Structurally Significant Items (SSIs),’’
dated July 15, 2004, of the British Aerospace
ATP AMM, as specified in paragraph (h) of
this AD. Do the initial inspection for fatigue
cracking at the applicable time in Part N.,
‘‘Approval,’’ of BAE SYSTEMS (Operations)
Limited Inspection Service Bulletin ATP–51–
002, Revision 3, dated April 3, 2008.
(o) Except as provided by paragraph (q) of
this AD: After the action specified in
paragraph (n) of this AD has been
accomplished, no alternative inspections or
inspection intervals may be approved for the
structural elements specified in the
documents listed in paragraph (n) of this AD.
(p) Submit a report of the findings (both
positive and negative) of all of the
inspections required by paragraph (n) of this
AD to Customer Engineering Liaison, BAE
SYSTEMS Regional Aircraft, Prestwick
International Airport, Ayrshire, KA9 2RW,
Scotland; telephone: +44 (0) 1292 675289;
fax: +44 (0) 1292 675432; at the applicable
time specified in paragraph (p)(1) or (p)(2) of
this AD. The report must include the
inspection results, a description of any
discrepancies found, the airplane serial
number, and the number of landings and
flight hours on the airplane.
(1) If the inspection was done on or after
the effective date of this AD: Submit the
report within 30 days after the inspection.
(2) If the inspection was done before the
effective date of this AD: Submit the report
within 30 days after the effective date of this
AD.
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue, SW., Renton, Washington 98057–
3356; telephone (425) 227–1175; fax (425)
227–1149. Before using any approved AMOC
on any airplane to which the AMOC applies,
notify your principal maintenance inspector
(PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal
inspector, your local Flight Standards District
Office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(3) Reporting Requirements: For any
reporting requirement in this AD, under the
provisions of the Paperwork Reduction Act
(44 U.S.C. 3501 et seq.), the Office of
Management and Budget (OMB) has
approved the information collection
requirements and has assigned OMB Control
Number 2120–0056.
FAA AD Differences
Related Information
Note 5: This AD differs from the MCAI
and/or service information as follows: No
differences.
(r) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2009–0074, dated
March 31, 2009; and BAE SYSTEMS
(Operations) Limited Inspection Service
Bulletin ATP–51–002, Revision 3, dated
April 3, 2008; for related information.
Other FAA AD Provisions
(q) The following provisions also apply to
this AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. Send
information to ATTN: Todd Thompson,
Material Incorporated by Reference
(s) You must use the service information
contained in Table 1 of this AD, as
applicable, to do the actions required by this
AD, unless the AD specifies otherwise.
TABLE 1—ALL MATERIAL INCORPORATED BY REFERENCE
Document
Revision
BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ....................................
BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ....................................
3 ................................
Original ......................
(1) The Director of the Federal Register
approved the incorporation by reference of
the service information contained in Table 2
Date
April 3, 2008.
December 20, 2005.
of this AD under 5 U.S.C. 552(a) and 1 CFR
part 51.
TABLE 2—NEW MATERIAL INCORPORATED BY REFERENCE
Document
Revision
jlentini on DSKJ8SOYB1PROD with RULES
BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ................................................
(2) The Director of the Federal Register
previously approved the incorporation by
reference of the service information
Date
3
April 3, 2008.
contained in Table 3 of this AD on September
21, 2006 (71 FR 52418, September 6, 2006).
TABLE 3—MATERIAL PREVIOUSLY INCORPORATED BY REFERENCE
Document
Revision
BAE SYSTEMS (Operations) Limited Service Bulletin ATP–51–002 ....................................
Original ......................
VerDate Nov<24>2008
16:14 Feb 24, 2010
Jkt 220001
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25FER1
Date
December 20, 2005.
Federal Register / Vol. 75, No. 37 / Thursday, February 25, 2010 / Rules and Regulations
(3) For service information identified in
this AD, contact BAE SYSTEMS Regional
Aircraft, 13850 McLearen Road, Herndon,
Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet
https://www.baesystems.com/Businesses/
RegionalAircraft/index.htm.
(4) You may review copies of the service
information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the
availability of this material at the FAA, call
425–227–1221 or 425–227–1152.
(5) You may also review copies of the
service information that is incorporated by
reference at the National Archives and
Records Administration (NARA). For
information on the availability of this
material at NARA, call 202–741–6030, or go
to: https://www.archives.gov/federal_register/
code_of_federal_regulations/
ibr_locations.html.
Issued in Renton, Washington, on February
16, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2010–3470 Filed 2–24–10; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2010–0131; Directorate
Identifier 2009–NM–132–AD; Amendment
39–16216; AD 2010–05–07]
RIN 2120–AA64
Airworthiness Directives; Airbus Model
A340–200 and A340–300 Series
Airplanes
AGENCY: Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for
comments.
jlentini on DSKJ8SOYB1PROD with RULES
SUMMARY: We are adopting a new
airworthiness directive (AD) for the
products listed above. This AD results
from mandatory continuing
airworthiness information (MCAI)
originated by an aviation authority of
another country to identify and correct
an unsafe condition on an aviation
product. The MCAI describes the unsafe
condition as:
A review of A340 missions has
demonstrated that CFM56–5C forward engine
mount thrust links fitted with oversized
bearing[s] will not reach the updated link
fatigue life limit of 15500 Flight Cycles (FC)
due to an increase in bore diameter.
* * * The consequent potential failure of
the affected thrust link would reduce the
forward engine mounts’ structural integrity
VerDate Nov<24>2008
16:14 Feb 24, 2010
Jkt 220001
and could eventually lead to engine
separation, constituting an unsafe condition.
*
*
*
*
*
This AD requires actions that are
intended to address the unsafe
condition described in the MCAI.
DATES: This AD becomes effective
March 12, 2010.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in the AD
as of March 12, 2010.
We must receive comments on this
AD by April 12, 2010.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue, SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–40, 1200 New Jersey Avenue, SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov; or in person at the
Docket Operations office between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
(800) 647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Vladimir Ulyanov, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue, SW., Renton,
Washington 98057–3356; telephone
(425) 227–1138; fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA
Airworthiness Directive 2009–0108,
dated May 5, 2009 (referred to after this
as ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
A review of A340 missions has
demonstrated that CFM56–5C forward engine
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
8471
mount thrust links fitted with oversized
bearing[s] will not reach the updated link
fatigue life limit of 15,500 Flight Cycles (FC)
due to an increase in bore diameter.
Oversized bearing repairs have been
possible through the accomplishment of
CMM 71–21–12 Repair 1. The consequent
potential failure of the affected thrust link
would reduce the forward engine mounts’
structural integrity and could eventually lead
to engine separation, constituting an unsafe
condition.
Consequently, this AD requires:
—The [detailed] inspection of the link
assembly to identify a possible oversized
bearing repair and, in case of finding, the
application of the associated corrective
actions, or
—The repetitive [detailed] inspection [for
cracking, damage (e.g., dents), and missing
fasteners] of the forward engine mounts
until accomplishment of the inspection of
the link assembly for the identification of
a possible oversized bearing repair.
The corrective actions for finding
oversized bearings in the forward engine
mount thrust link assembly include
contacting Goodrich for instructions and
doing the repair. The corrective actions
for finding cracking, damage (e.g.,
dents), and missing fasteners in the
forward engine mounts include,
depending on the findings, replacing
cracked parts and missing fasteners, and
polishing damaged areas. You may
obtain further information by examining
the MCAI in the AD docket.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A340–71–4007, including
Appendix 1, dated April 1, 2009. The
actions described in this service
information are intended to correct the
unsafe condition identified in the
MCAI.
FAA’s Determination and Requirements
of This AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are issuing this
AD because we evaluated all pertinent
information and determined the unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
There are no products of this type
currently registered in the United States.
However, this rule is necessary to
ensure that the described unsafe
condition is addressed if any of these
products are placed on the U.S. Register
in the future.
E:\FR\FM\25FER1.SGM
25FER1
Agencies
[Federal Register Volume 75, Number 37 (Thursday, February 25, 2010)]
[Rules and Regulations]
[Pages 8467-8471]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-3470]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD;
Amendment 39-16214; AD 2010-05-05]
RIN 2120-AA64
Airworthiness Directives; BAE SYSTEMS (Operations) Limited Model
ATP Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for the
products listed above that would supersede an existing AD. This AD
results from mandatory continuing airworthiness information (MCAI)
originated by an aviation authority of another country to identify and
correct an unsafe condition on an aviation product. The MCAI describes
the unsafe condition as:
A review of the results of the final fuselage fatigue test
identified the need for additional and revised safety-related
fatigue- and environmental inspections for the fuselage. These
additional tasks were introduced by Service Bulletin (SB) ATP-51-002
* * *.
As it was determined that these inspections were necessary to
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued * * *.
Since the original Issue of the SB, three revisions have been
published. Revision 1 of the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage frame designations in
Parts 50 and 50A and extended the allowable time before initial
inspection. In addition, the repeat inspection interval in Part 43
of the SB was reduced. In the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has been clarified.
* * * * *
The unsafe condition is fatigue cracking of certain structural
elements, which could result in reduced structural integrity of the
airplane and consequent rapid decompression of the airplane. This AD
requires actions that are intended to address the unsafe condition
described in the MCAI.
DATES: This AD becomes effective March 12, 2010.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in the AD as of March 12,
2010.
On September 21, 2006 (71 FR 52418, September 6, 2006), the
Director of the Federal Register approved the incorporation by
reference of a certain other publication listed in this AD.
We must receive comments on this AD by April 12, 2010.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue, SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue, SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov; or in person at the Docket Operations office
between 9 a.m. and 5 p.m., Monday through Friday, except Federal
holidays. The AD docket contains this AD, the regulatory evaluation,
any comments received, and other information. The street address for
the Docket Operations office (telephone (800) 647-5527) is in the
ADDRESSES section. Comments will be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT: Todd Thompson, International Branch,
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425) 227-
1149.
SUPPLEMENTARY INFORMATION:
Discussion
On July 15, 2007, we issued AD 2007-15-08, Amendment 39-15137 (72
FR 40230, July 24, 2007). That AD required actions intended to address
an unsafe condition on the products listed above.
Since we issued AD 2007-15-08, the European Aviation Safety Agency
(EASA), which is the Technical Agent for the Member States of the
European Community, has issued EASA Airworthiness Directive 2009-0074,
dated March 31, 2009 (referred to after this as ``the MCAI''), to
correct an unsafe condition for the specified products. The MCAI
states:
A review of the results of the final fuselage fatigue test
identified the need for additional and revised safety-related
fatigue- and environmental inspections for the fuselage. These
additional tasks were introduced by Service Bulletin (SB) ATP-51-
002, which supplemented and in some cases revised those previously
published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17
and the Maintenance Review Board Report (MRBR).
As it was determined that these inspections were necessary to
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued to require
the inspections and, depending on findings, corrective actions as
defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB)
at original issue.
Since the original Issue of the SB, three revisions have been
published. Revision 1 of the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage frame designations in
Parts 50 and 50A and extended the allowable time before initial
[[Page 8468]]
inspection. In addition, the repeat inspection interval in Part 43
of the SB was reduced. In the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has been clarified.
Fatigue tasks in Parts 1 through 50 of the SB, i.e. those
without an ``A'' suffix, have now been replicated in AMM Chapter 05-
10-17 and MRBR Section 6. In addition, environmental tasks, those
identified with an ``A'' suffix, have now been replicated in MRBR
Section 6.
For the reasons described above, this AD retains the
requirements of EASA AD 2006-0090, which is superseded, and requires
the accomplishment of the inspections and, depending on findings,
corrective actions as defined in BAE Systems (Operations) Limited SB
ATP-51-002 at Revision 3.
The unsafe condition is fatigue cracking of certain structural
elements, which could result in reduced structural integrity of the
airplane and consequent rapid decompression of the airplane. The
corrective actions include repairing cracking and corrosion, and
depending on findings, repairing or replacing damaged components. You
may obtain further information by examining the MCAI in the AD docket.
Relevant Service Information
BAE SYSTEMS (Operations) Limited has issued Service Bulletin ATP-
51-002, Revision 3, dated April 3, 2008. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are issuing this AD because we
evaluated all pertinent information and determined the unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
There are no products of this type currently registered in the
United States. However, this rule is necessary to ensure that the
described unsafe condition is addressed if any of these products are
placed on the U.S. Register in the future.
Differences Between the AD and the MCAI or Service Information
We have reviewed the MCAI and related service information and, in
general, agree with their substance. But we might have found it
necessary to use different words from those in the MCAI to ensure the
AD is clear for U.S. operators and is enforceable. In making these
changes, we do not intend to differ substantively from the information
provided in the MCAI and related service information.
We might also have required different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a NOTE within the AD.
Change to Existing AD
This AD retains all requirements of AD 2007-15-08. Since AD 2007-
15-08 was issued, the AD format has been revised, and certain
paragraphs have been rearranged. As a result, the corresponding
paragraph identifiers have changed in this AD, as listed in the
following table:
Revised Paragraph Identifiers
------------------------------------------------------------------------
Corresponding requirement in this
Requirement in AD 2007-15-08 AD
------------------------------------------------------------------------
paragraph (f) paragraph (g).
paragraph (g) paragraph (h).
paragraph (h) paragraph (i).
paragraph (i) paragraph (j).
paragraph (j) paragraph (k).
paragraph (k) paragraph (l).
------------------------------------------------------------------------
FAA's Determination of the Effective Date
Since there are currently no domestic operators of this product,
notice and opportunity for public comment before issuing this AD are
unnecessary.
Comments Invited
This AD is a final rule that involves requirements affecting flight
safety, and we did not precede it by notice and opportunity for public
comment. We invite you to send any written relevant data, views, or
arguments about this AD. Send your comments to an address listed under
the ADDRESSES section. Include ``Docket No. FAA-2010-0130; Directorate
Identifier 2009-NM-087-AD'' at the beginning of your comments. We
specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this AD. We will consider all
comments received by the closing date and may amend this AD because of
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this AD.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979); and
3. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
0
Accordingly, under the authority delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
[[Page 8469]]
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Amendment 39-15137 (72 FR
40230, July 24, 2007) and adding the following new AD:
2010-05-05 BAE Systems (Operations) Limited: Amendment 39-16214.
Docket No. FAA-2010-0130; Directorate Identifier 2009-NM-087-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective March
12, 2010.
Affected ADs
(b) This AD supersedes AD 2007-15-08, Amendment 39-15137.
Applicability
(c) This AD applies to all BAE Systems (Operations) Limited
Model ATP airplanes, certificated in any category.
Note 1: This AD requires revisions to certain operator
maintenance documents to include new and revised inspections.
Compliance with these inspections is required by 14 CFR 91.403(c).
For airplanes that have been previously modified, altered, or
repaired in the areas addressed by these inspections, the operator
may not be able to accomplish the inspections described in the
revisions. In this situation, to comply with 14 CFR 91.403(c), the
operator must request approval for an alternative method of
compliance according to paragraph (q) of this AD. The request should
include a description of changes to the required inspections that
will ensure the continued damage tolerance of the affected
structure. The FAA has provided guidance for this determination in
Advisory Circular (AC) 25-1529.
Subject
(d) Air Transport Association (ATA) of America Code: 51:
Standard Practices/Procedures.
Reason
(e) The mandatory continued airworthiness information (MCAI)
states:
A review of the results of the final fuselage fatigue test
identified the need for additional and revised safety-related
fatigue- and environmental inspections for the fuselage. These
additional tasks were introduced by Service Bulletin (SB) ATP-51-
002, which supplemented and in some cases revised those previously
published in the Aircraft Maintenance Manual (AMM) Chapter 05-10-17
and the Maintenance Review Board Report (MRBR).
As it was determined that these inspections were necessary to
maintain the structural integrity of the aeroplane, EASA AD 2006-
0090 [which corresponds to FAA AD 2007-15-08] was issued to require
the inspections and, depending on findings, corrective actions as
defined in BAE Systems (Operations) Limited SB ATP-51-002 (the SB)
at original issue.
Since the original Issue of the SB, three revisions have been
published. Revision 1 of the SB included only editorial changes.
Revision 2 of the SB corrected the fuselage frame designations in
Parts 50 and 50A and extended the allowable time before initial
inspection. In addition, the repeat inspection interval in Part 43
of the SB was reduced. In the latest Revision 3 of the SB, the grace
period for the initial inspection in Part 50 has been clarified.
Fatigue tasks in Parts 1 through 50 of the SB, i.e. those
without an ``A'' suffix, have now been replicated in AMM Chapter 05-
10-17 and MRBR Section 6. In addition, environmental tasks, those
identified with an ``A'' suffix, have now been replicated in MRBR
Section 6.
For the reasons described above, this AD retains the
requirements of EASA AD 2006-0090, which is superseded, and requires
the accomplishment of the inspections and, depending on findings,
corrective actions as defined in BAE Systems (Operations) Limited SB
ATP-51-002 at Revision 3.
The unsafe condition is fatigue cracking of certain structural
elements, which could result in reduced structural integrity of the
airplane and consequent rapid decompression of the airplane. The
corrective actions include repairing cracking and corrosion, and
depending on findings, repairing or replacing damaged components.
Compliance
(f) You are responsible for having the actions required by this
AD performed within the compliance times specified, unless the
actions have already been done.
Restatement of Requirements of AD 2006-18-09, With Revised Compliance
Method
Airworthiness Limitations Revision Specified in AD 2000-26-10
(g) Within 30 days after February 7, 2001 (the effective date of
AD 2000-26-10, Amendment 39-12060, which was superseded by AD 2005-
19-03, which was superseded by AD 2007-15-08), revise the
Airworthiness Limitations Section (ALS) of the Instructions for
Continued Airworthiness according to a method approved by the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA. Doing the revision specified in paragraph (h) of
this AD replaces Chapters 27, 32, 53, and 54 listed in Section 05-
10-11 and Chapters 52, 53, 54, 55, and 57 listed in Section 05-10-17
that are in effect on February 7, 2001, with Chapters 27, 32, 53,
and 54 listed in Section 05-10-11, ``Mandatory Life Limitations
(Airframe)''; and Chapters 52, 53, 54, 55, and 57 listed in Section
05-10-17, ``Structurally Significant Items (SSIs)''; both dated July
15, 2004; of the British Aerospace ATP Aircraft Maintenance Manual
(AMM). Doing the revision specified in paragraph (l) of this AD
replaces Sections 05-10-12, 05-10-15, and 05-10-17 with the
corresponding sections specified in paragraph (l) of this AD.
Note 2: Guidance on revising the ALS can be found in Section 05-
00-00, dated August 15, 1997, of the British Aerospace ATP AMM,
dated October 15, 1999. This section references other chapters of
the AMM. The applicable revision level of the referenced chapters is
that in effect on February 7, 2001.
Airworthiness Limitations Specified in AD 2005-19-03
(h) Within 30 days after September 28, 2005 (the effective date
of AD 2005-19-03, Amendment 39-14268, which was superseded by AD
2006-18-09), revise the ALS of the Instructions for Continued
Airworthiness according to a method approved by the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA.
Doing the revision specified in paragraph (i) of this AD replaces
certain Chapter 52 and 53 tasks listed in Section 05-10-17,
``Structurally Significant Items (SSIs),'' dated July 15, 2004, of
the British Aerospace ATP AMM, with the corresponding Chapter 52 and
53 tasks listed in BAE SYSTEMS (Operations) Limited Service Bulletin
ATP-51-002, dated December 20, 2005. Doing the revision specified in
paragraph (l) of this AD replaces Chapters 52, 53, 54, 55, and 57
listed in Section 05-10-17 with the corresponding Section 05-10-17
specified in paragraph (l) of this AD.
Note 3: Guidance on revising the ALS can be found in Chapters
27, 32, 53, and 54 listed in Section 05-10-11, ``Mandatory Life
Limitations (Airframe)''; and the tasks for Chapters 52, 53, 54, 55,
and 57 listed in Section 05-10-17, ``Structurally Significant Items
(SSIs)''; both dated July 15, 2004; of the British Aerospace ATP
AMM. These chapters replace the corresponding chapters in Section
05-00-00, dated August 15, 1997, of the British Aerospace ATP AMM as
specified in paragraph (g) of this AD.
New and Revised Airworthiness Limitations in AD 2006-18-09
(i) Within 30 days after September 21, 2006 (the effective date
of AD 2006-18-09), revise the ALS of the Instructions for Continued
Airworthiness by incorporating the new and revised tasks for
Chapters 52 and 53 as specified in BAE SYSTEMS (Operations) Limited
Service Bulletin ATP-51-002, dated December 20, 2005, into the ALS.
The revised Chapter 52 and 53 tasks replace the corresponding
Chapter 52 and 53 tasks in Section 05-10-17, ``Structurally
Significant Items (SSIs),'' dated July 15, 2004, of the British
Aerospace ATP AMM, as specified in paragraph (h) of this AD.
(j) Except as provided by paragraph (q) of this AD: After the
actions specified in paragraphs (g), (h), and (i) of this AD have
been accomplished, no alternative inspections or inspection
intervals may be approved for the structural elements specified in
the documents listed in paragraphs (g), (h), and (i) of this AD.
No Reporting Required
(k) Although BAE SYSTEMS (Operations) Limited Service Bulletin
ATP-51-002, dated December 20, 2005, specifies to submit certain
information to the manufacturer, this AD does not include that
requirement.
Restatement of Requirements of AD 2007-15-08, With Revised Compliance
Method
Revised Limitations
(l) Within 30 days after August 8, 2007 (the effective date of
AD 2007-15-08), revise the
[[Page 8470]]
ALS of the Instructions for Continued Airworthiness according to a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA.
Note 4: Guidance on revising the ALS can be found in Section 05-
10-12, ``Mandatory Life Limitations (Airframe--Structures),'' dated
January 15, 2007; Section 05-10-15, ``Mandatory Life Limitations
(Powerplant/Engine/APU--Structures),'' dated January 15, 2007; and
Section 05-10-17, ``Structurally Significant Items (SSIs),'' dated
January 15, 2007; of the BAE Systems (Operations) Limited ATP AMM.
The revised sections replace the corresponding sections specified in
paragraphs (g) and (h) of this AD.
(m) Except as provided by paragraph (q) of this AD: After the
action specified in paragraph (l) of this AD has been accomplished,
no alternative inspections or inspection intervals may be approved
for the structural elements specified in the documents listed in
paragraph (l) of this AD.
New Requirements of This AD
Actions
(n) Within 30 days after the effective date of this AD: Revise
the ALS of the Instructions for Continued Airworthiness by
incorporating the inspections specified in BAE SYSTEMS (Operations)
Limited Inspection Service Bulletin ATP-51-002, Revision 3, dated
April 3, 2008. Doing this revision terminates the requirements of
paragraph (i) of this AD. The revised Chapter 52 and 53 tasks
replace the corresponding Chapter 52 and 53 tasks in Section 05-10-
17, ``Structurally Significant Items (SSIs),'' dated July 15, 2004,
of the British Aerospace ATP AMM, as specified in paragraph (h) of
this AD. Do the initial inspection for fatigue cracking at the
applicable time in Part N., ``Approval,'' of BAE SYSTEMS
(Operations) Limited Inspection Service Bulletin ATP-51-002,
Revision 3, dated April 3, 2008.
(o) Except as provided by paragraph (q) of this AD: After the
action specified in paragraph (n) of this AD has been accomplished,
no alternative inspections or inspection intervals may be approved
for the structural elements specified in the documents listed in
paragraph (n) of this AD.
(p) Submit a report of the findings (both positive and negative)
of all of the inspections required by paragraph (n) of this AD to
Customer Engineering Liaison, BAE SYSTEMS Regional Aircraft,
Prestwick International Airport, Ayrshire, KA9 2RW, Scotland;
telephone: +44 (0) 1292 675289; fax: +44 (0) 1292 675432; at the
applicable time specified in paragraph (p)(1) or (p)(2) of this AD.
The report must include the inspection results, a description of any
discrepancies found, the airplane serial number, and the number of
landings and flight hours on the airplane.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
FAA AD Differences
Note 5: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(q) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, FAA, has the authority to approve AMOCs for
this AD, if requested using the procedures found in 14 CFR 39.19.
Send information to ATTN: Todd Thompson, International Branch, ANM-
116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW.,
Renton, Washington 98057-3356; telephone (425) 227-1175; fax (425)
227-1149. Before using any approved AMOC on any airplane to which
the AMOC applies, notify your principal maintenance inspector (PMI)
or principal avionics inspector (PAI), as appropriate, or lacking a
principal inspector, your local Flight Standards District Office.
The AMOC approval letter must specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) Reporting Requirements: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(r) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2009-0074, dated March 31, 2009;
and BAE SYSTEMS (Operations) Limited Inspection Service Bulletin
ATP-51-002, Revision 3, dated April 3, 2008; for related
information.
Material Incorporated by Reference
(s) You must use the service information contained in Table 1 of
this AD, as applicable, to do the actions required by this AD,
unless the AD specifies otherwise.
Table 1--All Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited 3................................ April 3, 2008.
Service Bulletin ATP-51-002.
BAE SYSTEMS (Operations) Limited Original......................... December 20, 2005.
Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
(1) The Director of the Federal Register approved the
incorporation by reference of the service information contained in
Table 2 of this AD under 5 U.S.C. 552(a) and 1 CFR part 51.
Table 2--New Material Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited Service 3 April 3, 2008.
Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
(2) The Director of the Federal Register previously approved
the incorporation by reference of the service information contained
in Table 3 of this AD on September 21, 2006 (71 FR 52418, September
6, 2006).
Table 3--Material Previously Incorporated by Reference
----------------------------------------------------------------------------------------------------------------
Document Revision Date
----------------------------------------------------------------------------------------------------------------
BAE SYSTEMS (Operations) Limited Original......................... December 20, 2005.
Service Bulletin ATP-51-002.
----------------------------------------------------------------------------------------------------------------
[[Page 8471]]
(3) For service information identified in this AD, contact BAE
SYSTEMS Regional Aircraft, 13850 McLearen Road, Herndon, Virginia
20171; telephone 703-736-1080; e-mail raebusiness@baesystems.com;
Internet https://www.baesystems.com/Businesses/RegionalAircraft/index.htm.
(4) You may review copies of the service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton,
Washington. For information on the availability of this material at
the FAA, call 425-227-1221 or 425-227-1152.
(5) You may also review copies of the service information that
is incorporated by reference at the National Archives and Records
Administration (NARA). For information on the availability of this
material at NARA, call 202-741-6030, or go to: https://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.
Issued in Renton, Washington, on February 16, 2010.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-3470 Filed 2-24-10; 8:45 am]
BILLING CODE 4910-13-P